Internal-combusstion engine



Sept. 7, 1948. w GIZARA 2,448,972

' INTERNALCOIBUSTION ENGINE (TURBINE TYPE) Filed Oct. 20, 1944 2 Sheets-Sheet 1 4 Inventor ZowA/ebh/ 6/2ARA, l

' 9 B Q4 wfinwey Mtg]:

p 7. 1948. E. w. GIZARA 2,448,972

INTERNAL-COMBUSTION ENGINE (TURBINE TYPE) Filed Oct. 20, 1944 2 Sheets-Sheet 2 Inventory 1014/4/90 h! 'G/ZARA,

I lk\\\\\\;\\\\\\\ l W nn; E

Attorneys Patented Sept. 7, 1948 UNITED STATES PATENT OFFICE INTERNAL-COMBUSTION ENGINE Edward W. Gilara, Amsterdam, N. Y.

, Application October 20, 1944, Serial No. 559,591

3 Claims. (Cl. 60-41) This invention relates to internal combustion engines and has for its object to provide a centrifugal feed turbine.

Another object of the invention is to provide a turbine in which combustion is continuous as long as the engine is in operation.

Another object of the invention is to provide a turbine in which all of the operating elements thereof are in one integral or fixed part.

A further object of the invention is to provide a turbine engine in which the casing, the propulsion vanes, the combustion chamber, the gas deflector, the air intake and distributor are fixedly mounted upon a driven power shaft and revolve therewith.

, Another object of the invention is to provide an internal combustion turbine the entire periphery of which forms an exhaust port.

A still further object of the invention is to provide in a turbine a large number of spaced vanes and means whereby pressure may be brought simultaneously upon all of said vanes.

Other features and advantages become more readily apparent from the following description and the accompanying drawings in which:

Figure l is a top plan view of my improved turbine,

Figure 2 is an end elevational view thereof,

Figure 3 is a sectional view taken on line 3-3 of Figure 1, and

Figure 4 is a vertical sectional view taken on line 84 of Figure 1.

Like reference characters indicate like parts throughout the .following specifications and in several views in the drawings in which ll indicates my turbine and H and I! are spaced apart bearings, the heads I! and H of which support the power shaft l5. To the free end ii of said shaft is aflixed a power takeoff pulley ll.

Integrally or fixedly carried on end ll of shaft I5 is a rotor it, formed of a pair ofinverted substantially W-shaped (in cross section) casing members II and 2 I, integrally connected by arcuate spaced apart vanes 22, which in elevation are fan shaped. The inner reduced ends II, of these vanes terminate at a substantially cylindrical, angular combustion chamber 24. Inwardly of said combustion chamber is another series of arcuate vanes 25, integrally formed on, or connecting the wall 20 and bame II. These latter vanes at their larger and inner ends 26, terminate in an atmospheric air inlet 21, at the center oi the wall II.

A substantially concave cone shaped bailie plate II, is fixed to the inner end II, of the shaft I5 and spaced lightly from the similarly formed portion 30 of the member 20, whereby an angular passage-way if is formed between said parts 28 and 30 and having an annular outlet 32 into the combustion chamber 24. The passageway ii is connected by a bore 33, extending transversely through the inner end of shaft l5, and connects with the longitudinal bore 34, running substantially through said shaft l5, and to the gas inlet chamber 35, formed in the arm 36, which is an integral extension of the member l2. The part 31 of shaft l5 which passes through arm 38 and chamber 35 is provided with a peripheral groove 38, connected by a port 39 with bore 34, whereby gas from feed pipe 40 to chamber 35 enters the bore 34.

Threaded in the outer wall portion ll of the combustion chamber 24 is a spark plug It, the point 43 of which is adapted to engage the contact ll supported on a bracket 45, attached to the base 45, upon which the members H and II are supported. An electric wire 41 conducts current to the contact 44.

In operation the turbine is very simple. It is first to be noted that the rotor which includes the side walls 20 and II, the driving vanes 22 and the baflle 25, the air intake vanes 25 and the shaft IS with its pulley II, are all formed into one single movable unit, no other elements of the invention move. To start the turbine it is only necessary to revolve said unit until spark plug 42 engages, that is brushes, the contact 44, causing a spark in the plug gap within the combustion chamber 24, thus igniting the gas and air mixture therein. The expansion of the gas presses upon all of the arcuate vanes 22 at one and the same time and during said expansion period forces its way to escape through the passages 48, separating the vanes, and in doing so presses upon the concave surfaces of the .vanes, thus driving the rotor. The rotation of the turbine draws gas into every part of the circular combustion chamber 24 through centrifugal action, and at the same time the fan formed by vanes 25 draws in atmospheric air through port 21 and drives it with force into the combustion chamber, thus forcedly mixing the air with, the incoming gas from inlet 32. After the turbine has once started the firing is continuous, no further electric spark being required as the fresh incoming gases are ignited by fire already in the chamher.

As there is just one movable unit with only two bearings lost motion is reduced to the very minimum, friction is reduced to a minimum to which this invention relates will be able to obtain a clear understanding of the invention after considering the description in connection with the drawing. Therefore, a more lengthy description is regarded as unnecessary.

Minor changes in shape, size and rearrangement of details and parts, such as come within the purview of the invention claimed, may be resorted to in actual practice, if desired.

Having'described my invention, that which I claim as new and desire to secure by Letters Patent is: v

1. A rotor all elements of which are integrally connected including a series of spaced vanes and means whereby pressure is simultaneously brought to bear upon all of said vanes, means whereby exhaust is provided for between each pair of said vanes, means whereby a fuel is fed to the rotor by centrifugal action, acombustion chamberformed in the rotor, a fan formed in the rotor, said chamber being located between the fan and the vanes, said chamber being substantially cylindrical in cross section and ring of spaced walls, said vanes connecting said walls, said baille plate fan and one or said walls being connected, a circular combustion chamber formed by said walls, and surrounding said fan. said vanes surrounding said combustion chamber, said bafile plate and one of the walls forming a circular gas feed space inlet to the combustion chamber.

3. A turbine formed of one piece including a casing, a series of drive vanes, a suction fan, a baflle plate, a shaft and a gas inlet all formed in one single unit, said casing comprising a pair of spaced walls, said vanes connecting said walls, said bafile plate fan and one of said walls being connected, a circular combustion chamber formed by said walls, and surrounding said fan, said vanes surrounding said combustion chamber. said baffle plate and one of the walls formin a circular gas feed space inlet to the combustion chamber, said shaft being tubular and providing a gas conduit to said feed space.

EDWARD W. GIZARA.

REFERENCES CITED The following references are of record in. the file of this patent:

UNITED STATES PATENTS Number Name Date.

FOREIGN PATENTS Country I Date Great Britain June 22,1922 France Mar. 25, 1908 Number Irgens Jan. 3, 1899 I 

